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Computation of Hinge-Moment Characteristics of Horizontal Tails from Section Data

Description: Bulletin presenting a study of data from various wind-tunnel tests of horizontal tail surfaces to determine the accuracy with which section data can be used to estimate the hinge-moment characteristics of control surfaces of finite span. The study consisted of a comparison between the variations of elevator hinge moments with elevator deflection and with airplane pitching moment, as estimated from data obtained in two-dimensional flow, and that variation measured experimentally on 16 different horizontal tails mounted on wind-tunnel models of complete airplanes.
Date: April 1945
Creator: Crane, Robert M.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of ailerons on a low-drag airfoil 1: The effect of aileron profile

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of various modifications to the profile of a 0.20-chord plain sealed aileron and a 0.15-chord plain sealed aileron on an NACA 66,2-216 airfoil. Thickening of the aileron was found to reduce the aileron effectiveness, reduce the slope of the wing section lift curve, and reduce the hinge-moment coefficients. Results regarding the section data, aileron effectiveness, aileron hinge moments, lift, pitching moment, drag, and Reynolds number are provided.
Date: January 1944
Creator: Crane, Robert M. & Holtzclaw, Ralph W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effects of profile modification and tabs on the characteristics of ailerons on a low-drag airfoil

Description: An investigation has been made to determine the effect of control-surface profile modifications on the aerodynamic characteristics of an NACA low-drag airfoil equipped with a 0.20-chord and a 0.15-chord aileron. Tab characteristics have been obtained for 0.20-aileron chord tabs on two of the 0.20-chord ailerons. Basic data are presented from which the effect of tabs can be calculated for specific cases. The data are sufficient for the solution of problems of fixed tabs with a differential linkage, as well as simple and spring-linked balancing tabs.
Date: 1944
Creator: Crane, Robert M. & Holtzclaw, Ralph W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of ailerons on a low-drag airfoil 2: the effect of thickened and beveled trailing edges

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of modifications to the trailing edge of a 0.20-chord plain sealed aileron on an NACA 66,2-216 airfoil. The modifications considered consisted of various amounts of symmetrical thickening and beveling of the aileron trailing edge. Results regarding aileron effectiveness, aileron hinge moments, aileron control forces, lift, pitching moment, drag, and Reynolds number are provided.
Date: January 1944
Creator: Crane, Robert M. & Holtzclaw, Ralph W.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Ailerons on a Low-Drag Airfoil 3: The Effect of Tabs

Description: Report presenting an investigation of the effects of 0.20-aileron-chord tabs on an NACA 66,2-216 airfoil equipped with a 0.20-airfoil-chord plain sealed aileron. Basic data are presented from which the effect of tabs can be calculated for specific cases. The data are sufficient for the solution of problems of fixed tabs with a differential linkage, as well as simple and spring-linked balancing tabs.
Date: November 1944
Creator: Holtzclaw, Ralph W. & Crane, Robert M.
Partner: UNT Libraries Government Documents Department